Research Papers

Rotating Instability in an Annular Cascade: Detailed Analysis of the Instationary Flow Phenomena

[+] Author and Article Information
Benjamin Pardowitz

German Aerospace Center (DLR),
Institute of Propulsion Technology,
Engine Acoustics Department,
Müller-Breslau-Straße 8,
Berlin 10623, Germany
e-mail: Benjamin.Pardowitz@dlr.de

Ulf Tapken, Lars Enghardt

German Aerospace Center (DLR),
Institute of Propulsion Technology,
Engine Acoustics Department,
Müller-Breslau-Straße 8,
Berlin 10623, Germany

Robert Sorge, Paul Uwe Thamsen

Technical University Berlin,
Fluiddynamics Department,
Straße des 17. Juni 135,
Berlin 10623, Germany

Institute for Aeronautics and Astronautics, Chair for Aero Engines.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 6, 2013; final manuscript received September 3, 2013; published online November 28, 2013. Editor: Ronald Bunker.

J. Turbomach 136(6), 061017 (Nov 28, 2013) (10 pages) Paper No: TURBO-13-1183; doi: 10.1115/1.4025734 History: Received August 06, 2013; Revised September 03, 2013

Rotating instability (RI) occurs at off-design conditions in compressors, predominantly in configurations with large tip or hub clearance ratios of s* 3%. RI is the source of the blade tip vortex noise and a potential indicator for critical operating conditions like rotating stall and surge. The objective of this paper is to give more physical insight into the RI phenomenon using the analysis results of combined near-field measurements with high-speed particle image velocimetry (PIV) and unsteady pressure sensors. The investigation was pursued on an annular cascade with hub clearance. Both the unsteady flow field next to the leading edge as well as the associated rotating pressure waves were captured. A special analysis method illustrates the characteristic pressure wave amplitude distribution, denoted as “modal events” of the RI. Moreover, the slightly adapted method reveals the unsteady flow structures corresponding to the RI. Correlations between the flow profile, the dominant vortex structures, and the rotating pressure waves were found. Results provide evidence to a new hypothesis, implying that shear layer instabilities constitute the basic mechanism of the RI.

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Mailach, R., LehmannI., and Vogeler, K., 2001, “Rotating Instabilities in an Axial Compressor Originating From the Fluctuating Blade Tip Vortex,” ASME J. Turbomach., 123, pp. 453–463. [CrossRef]
Liu, J. M., Holste, F., and Neise, W., 1996, “On the Azimuthal Mode Structure of Rotating Blade Flow Instabilities in Axial Turbomachines,” 2nd AIAA/CEAS Aeroacoustics Conference, State College, PA, May 6–8, AIAA Paper No. 96-1741 [CrossRef].
März, J., Hah, C., and Neise, W., 2002, “An Experimental and Numerical Investigation Into the Mechanisms of Rotating Instability,” ASME J. Turbomach., 124, pp. 367–365. [CrossRef]
Neuhaus, L., and Neise, W., 2003, “Active Flow Control to Reduce the Tip Clearance Noise and Improve the Aerodynamic Performance of Axial Turbomachines,” Fan Noise 2003: 2nd International Symposium, Senlis, France, September 23–25.
Kameier, F., and Neise, W., 1997, “Rotating Blade Flow Instability as a Source of Noise in Axial Turbomachines,” J. Sound Vib., 203, pp. 833–853. [CrossRef]
Fukano, T., Takamatsu, Y., and Kodama, Y., 1986, “The Effects of Tip Clearance on the Noise of Low Pressure Axial and Mixed Flow Fans,” J. Sound Vib., 105, pp. 291–308. [CrossRef]
Kameier, F., and Haukap, C., 2001, “Experimentelle Untersuchungen strömungserregter Schaufelschwingungen bei Axialverdichtern,” FH Düsseldorf, Progress Report.
Haukap, C., 2005, “Zur Korrelation von Schaufelschwingungen und rotierenden Strömungsphänomenen in Axialverdichtern,” Ph.D. thesis, Technical University Munich, Munich, Germany.
Truckenmüller, F., 2003, “Untersuchungen zur aerodynamisch induzierten Schwingungsanregung von Niederdruck-Laufschaufeln bei extremer Teillast,” Ph.D. thesis, Universität Stuttgart, Stuttgart, Germany.
Zhang, L. Y., He, L., and Stuer, H., 2011, “A Numerical Investigation of Rotating Instability in Steam Turbine Last Stage,” ASME Conf. Proc., 2011(54679), pp. 1657–1666.
Raitor, T., and Neise, W., 2008, “Sound Generation in Centrifugal Compressors,” J. Sound Vib., 314(3–5), pp. 738–756. [CrossRef]
Inoue, M., Kuroumaru, M., Yoshida, S., Minami, T., Yamada, K., and Furukawa, M., 2004, “Effect of Tip Clearance on Stall Evolution Process in a Low-Speed Axial Compressor Stage,” ASME Paper No. GT2004-53354 [CrossRef].
Pardowitz, B., Tapken, U., and Enghardt, L., 2012, “Time-Resolved Rotating Instability Waves in an Annular Cascade,” 18th AIAA/CEAS Aeroacoustics Conference, Colorado Springs, CO, June, 4–6, AIAA Paper No. 2012-2132 [CrossRef].
Pardowitz, B., Tapken, U., and Enghardt, L., 2012, “Acoustic Resonances and Aerodynamic Interactions in an Axial Compressor Stator Stage Test Rig,” 10th International Conference on Flow-Induced Vibration (& Flow-Induced Noise), Dublin, Ireland, July 3–7.
Beselt, Ch., Rennings, R., Thiele, F., and Peitsch, D., 2012, “Experimental and Numerical Investigation of Rotating Instability Phenomenon in an Axial Compressor Stator,” 42nd AIAA Fluid Dynamics Conference, New Orleans, LA, June 25–28, AIAA Paper No. 2012-2980 [CrossRef].
Ulbricht, I., 2002, “Stabilität des stehenden Ringgitters,” Ph.D. thesis, Technical University Berlin, Berlin, Germany.
Beselt, Chr., Peitsch, D., Pardowitz, B., and Enghardt, L., 2011, “Strömungsinduzierter Schall in Turbomaschinen—Die Rotierende Instabilität,” 60th German Air and Space Congress, Bremen, Germany, September 27–29, Paper No. ID-241377.
Neuhaus, L., and Neise, W., 2002, “Active Control of the Aerodynamic and Acoustic Performance,” 8th AIAA/CEAS Aeroacoustics Conference, Breckenridge, CO, June 17–19, AIAA Paper No. 2002–2499 [CrossRef].
Neuhaus, L., and Neise, W., 2005, “Active Control to Improve the Aerodynamic Performance and Reduce the Tip Clearance Noise of Axial Turbomachines,” 11th AIAA/CEAS Aeroacoustics Conference (26th AIAA Aeroacoustics Conference), Monterey, CA, May 23–25, AIAA Paper No. 2005-3073 [CrossRef].
Schrapp, H., 2008, “Experimentelle Untersuchungen zum Aufplatzen des Spaltwirbels in Axialverdichtern,” Ph.D. thesis, Technical University Braunschweig, Brunswick, Germany.
Kameier, F., 1993, “Experimentelle Untersuchung zur Entstehung und Minderung des Blattspitzen-Wirbellärms axialer Strömungsmaschinen,” Ph.D. thesis, Technical University Berlin, Berlin, Germany.
Sijtsma, P., and Zillmann, J., 2007, “In-Duct and Far-Field Mode Detection Techniques for Engine Exhaust Noise Measurements,” 13th AIAA/CEAS Aeroacoustics Conference, Rome, May 21–23, AIAA Paper No. 2007-3439 [CrossRef].
Jürgens, W., Tapken, U., Pardowitz, B., Kausche, P., Bennett, G. J., and Enghardt, L., 2010, “Technique to Analyze Characteristics of Turbomachinery Broadband Noise Sources,” 16th AIAA/CEAS Aeroacoustic Conference, Stockholm, Sweden, June 7–9, AIAA Paper No. 2010-3979 [CrossRef].
Mugridge, B., 1969, “The Measurement of Spinning Acoustic Modes Generated in an Axial Flow Fan,” J. Sound Vib., 10(2), pp. 227–246. [CrossRef]
Mailach, R., 2001, “Experimentelle Untersuchung von Strömungsinstabilitäten im Betriebsbereich zwischen Auslegungspunkt und Stabilitätsgrenze eines vierstufigen Niedergeschwindigkeits-Axialverdichter,” Ph.D. thesis, Technical University Dresden, Dresden, Germany.
Vo, H. D., Tan, C. S., and Greitzer, E. M., 2008, “Criteria for Spike Initiated Rotating Stall,” ASME J. Turbomach., 130(1), p. 011023. [CrossRef]
Beselt, Ch., Pardowitz, B., van Rennings, R., Sorge, R., Peitsch, D., Enghardt, L., Thiele, F., Ehrenfried, K., and Thamsen, P.-U., 2013, “Influence of the Clearance Size on Rotating Instability in an Axial Compressor Stator,” 10th European Turbomachinery Conference, Lappeenranta, Finland, April 15–19.
van Rennings, R., Shi, K., Fu, S., and Thiele, F., 2012, “Delayed-Detached-Eddy Simulation of Near-Stall Axial Compressor Flow With Varying Passage Numbers,” Notes on Numerical Fluid Mechanics and Multidisciplinary Design (Progress in Hybrid RANS-LES Modelling, Vol. 117), Springer-Verlag, Berlin, pp. 439–448.


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Fig. 4

Averaged 2D flow fields in the annular cascade measured tangentially at the hub (radius ri=86 mm) for two incidence angles i1=+8 deg (top) and i2=+11 deg (bottom). Labeled positions (◻), see Fig. 5.

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Fig. 3

Positioning of the high-speed PIV system at the annular cascade

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Fig. 2

Meridional view of the test section with radial dimensions (units: mm)

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Fig. 1

Integrated measurement equipment in the annular compressor cascade (unsteady pressure sensors and high-speed PIV)

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Fig. 5

Radial profiles of the axial and azimuthal velocities for both flow incidence angles of i=+8 deg (left) and i=+11 deg (right) determined at the position x=514 mm and y=0 mm in Fig. 4

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Fig. 6

Spectral analysis of the unsteady flow field. Power spectral densities of velocity fluctuations measured with high-speed PIV (top). Circumferential mode amplitudes deduced from the pressure measurements (bottom).

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Fig. 8

Identified triggers N depending on the amplitude threshold Thrm and phase range ΦΔ for the analysis of 10 s of pressure data

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Fig. 9

Visualization of a modal event of the RI mode m = 5 using the analysis procedure (step 1–3) applied to the pressure data

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Fig. 7

Amplitude distribution of the dominant RI mode of order m = 5 based on the time-resolved mode analysis using the pressure measurements

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Fig. 11

Filtered velocity fluctuations at two monitor regions I (solid lines) and II (dashed lines) with its magnitude (top), axial (middle), and tangential velocity components (bottom)

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Fig. 12

Number of identified triggers N depending on the amplitude threshold A'Thr and a phase range αΔ

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Fig. 13

Period of the unsteady flow field in correspondence to the RI mode m = 5 (see Fig. 14) at radius r = 86 mm (Nomenclature as in Fig. 10)

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Fig. 14

Unsteady pressure field of the modal event triggered by the dominant RI mode m = 5 corresponding to Fig. 13 (a single passage is highlighted; Nomenclature as in Fig. 9)

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Fig. 10

Exemplary unsteady flow field at a radial position of r = 86 mm (next to the hub) for operating conditions where the RI is present




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